Abstract: The aeroelastic property of a wing can be improved by using the bending-twisting coupling effect of composite material skin. A genetic algorithm approach was employed to optimize this type structure in order to maximize the effect of bending twisting coupling and a sandwich structure to be an analysis example. A finite element software was used to analysis the objective function, the strength of the sandwich structure were used as the restriction function. The genetic algorithms optimum and finite element analysis function were integrated so that a structure optimal software was developed for complex structure optimization.